DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Privacy Policy | Contact | Deutsch
Fontsize: [-] Text [+]

A parametric aircraft fuselage model for preliminary sizing and crashworthiness applications

Schwinn, Dominik and Kohlgrüber, Dieter and Scherer, Julian and Siemann, Martin (2016) A parametric aircraft fuselage model for preliminary sizing and crashworthiness applications. CEAS Aeronautical Journal, 7 (3), pp. 357-372. Springer. doi: 10.1007/s13272-016-0193-4. ISSN 1869-5590.

Full text not available from this repository.

Official URL: http://link.springer.com/article/10.1007/s13272-016-0193-4


The aircraft design process generally comprises three consecutive phases: conceptual, preliminary and detailed design phase. In the conceptual design phase a basis aircraft layout is defined using multidisciplinary analysis procedures. For the structural layout, however, the preliminary design phase is of particular interest as more detailed calculations are introduced to enhance the basic design of the primary structure. Up to date, semi-analytical methods are widely used in this design stage to estimate the structural mass. Although these methods lead to adequate results for the major aircraft components of standard configurations, the evaluation of new configurations (e.g., box wing, blended wing body) or specific structural components with complex loading conditions (e.g., center wing box) is very challenging and demands higher fidelity approaches based on Finite Elements (FE). To accelerate FE model generation in a multidisciplinary design environment, automated processes based on a parametric model description have been introduced. To easily couple in- and output of different tools, a standardized data format - CPACS (Common Parametric Aircraft Configuration Schema) - is used. The versatile structural description in CPACS, the implementation in model generation tools, but also current limitations and future enhancements will be discussed. Recent development on the progress of numerical process chains for structural sizing and crashworthiness applications on solid ground and on water (ditching) are presented in this paper.

Item URL in elib:https://elib.dlr.de/105659/
Document Type:Article
Title:A parametric aircraft fuselage model for preliminary sizing and crashworthiness applications
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Schwinn, DominikUNSPECIFIEDhttps://orcid.org/0000-0003-2341-9632UNSPECIFIED
Kohlgrüber, DieterUNSPECIFIEDhttps://orcid.org/0000-0002-6626-0927UNSPECIFIED
Scherer, JulianUNSPECIFIEDhttps://orcid.org/0000-0002-8054-4686UNSPECIFIED
Siemann, MartinUNSPECIFIEDhttps://orcid.org/0000-0002-7213-0715UNSPECIFIED
Journal or Publication Title:CEAS Aeronautical Journal
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Page Range:pp. 357-372
Keywords:structural design; fuselage sizing; crashworthiness; multidisciplinary analysis; parametric modeling
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:fixed-wing aircraft
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Structures and Materials (old)
Location: Stuttgart
Institutes and Institutions:Institute of Structures and Design > Structural Integrity
Deposited By: Schwinn, Dominik
Deposited On:01 Dec 2016 11:12
Last Modified:21 Nov 2023 10:32

Repository Staff Only: item control page

Help & Contact
electronic library is running on EPrints 3.3.12
Website and database design: Copyright © German Aerospace Center (DLR). All rights reserved.